Path: Orbit/OrbitMechanics
% Propagates the NORAD two line elements, ex. SGP, SGP4, SGP8.
SGP4 output is in the TEME frame - true equator, mean equinox.
file can be a file name or a string input. The string must have the
same format as the file for example:
s = [sprintf('SGPTest \n'),...
sprintf('1 88888U 80275.98708465 .00073094 13844-3 66816-4 0 8\n'),...
sprintf('2 88888 72.8435 115.9689 0086731 52.6988 110.5714 16.05824518 105')];
See also NORAD, LoadNORAD, ConvertNORAD.
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Form:
[r,v,x] = PropagateTLE( tVec, file, model )
[r,v,x] = PropagateTLE( tVec, x, model )
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Inputs
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tVec (1,:) Time vector (sec)
file (1,:) File name OR converted data structure
model (1,:) Model type 'SGP', 'SGP4', 'SDP4', 'SGP8', 'SGD8'
The default model is SGP4.
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Outputs
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r (3,:) or {:} Position vectors
v (3,:) or {:} Velocity vectors
x (:) Structure of NORAD element data
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References: Hoots, F. R. and R. L. Roehrich, "Spacetrack Report No. 3:
Models for Propagation of NORAD Element Sets", Dec. 1980.
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Orbit: OrbitCoord/ConvertNORAD SC: Ephem/GMSTime
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